CN110412462B - Transient temperature prediction method for permanent magnet synchronous motor for aviation - Google Patents
Transient temperature prediction method for permanent magnet synchronous motor for aviation Download PDFInfo
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Abstract
The invention provides a transient temperature prediction method of an aeronautical permanent magnet synchronous motor, which is characterized in that a two-dimensional electromagnetic field design is carried out on the motor according to the geometric dimension, material parameters, a working system and load characteristics of the motor, corresponding electromagnetic parameters are obtained, a three-phase current and motor rotating speed curve of the motor is obtained through Matlab/Simulink electric drive system simulation analysis, and the transient temperature prediction is carried out on the temperature distribution of each part of the motor based on curve fitting, loss calculation of a current source method/voltage source method, three-dimensional model design and finite element model grid division of the motor, cooling and heat dissipation conditions and fluid-solid coupling analysis, and the temperature distribution of each part of the motor, so that high-precision temperature distribution is obtained, and the assistance is provided for the.
Description
Technical Field
The invention relates to the technical field of permanent magnet synchronous motor simulation, in particular to a transient temperature prediction method for an aviation permanent magnet synchronous motor.
Background
The high power density of the motor is an important index for measuring the design of the motor, and because the power density of the motor is very high, the motor can bear two times or even three times of overload when being started, braked or under special working conditions, and even if the working time of the motor is short under the working conditions, the temperature of the stator winding can be rapidly increased due to the large current in the stator winding, so that insulation damage and motor burnout can be caused. And high power density permanent magnet synchronous motor has the high-speed high frequency's characteristic, and high-speed high frequency can lead to stator core's hysteresis loss, eddy current loss and the eddy current loss greatly increased of magnet, even the motor works for a short time still can lead to stator core and permanent magnet to have very high temperature rise. In addition, the permanent magnet synchronous motor for aviation is also subjected to high ambient temperature, which is 70 ℃ in most cases, and even as high as 130 ℃ in some cases.
Therefore, the extreme temperature rise of the stator winding, the stator core and the permanent magnet becomes a key factor for restricting the further improvement of the power density of the permanent magnet synchronous motor for aviation, so that the temperature field analysis of the motor needs to be carried out by means of simulation analysis software in the detailed design stage, and the distribution condition of the working temperature of the motor is obtained.
At present, simulation analysis software is adopted to analyze the temperature field of the motor, and mainly aims at a fuel pump motor and an environment-controlled pump motor which work for a long time to control the motor. For a long-time working motor, most of the time is in a steady-state working stage, so that only the stator winding copper loss, the stator core loss, the permanent magnet eddy current loss, the wind friction loss of a rotor assembly and the friction loss at a bearing of the motor in a stable working state are calculated in the simulation process, and the temperature field analysis is carried out on the motor according to the loss result obtained by calculation.
The method is based on a three-dimensional model of the motor and adopts ICEM or Gambit to perform non-structural grid division on the motor to complete temperature prediction under a steady-state working state of the motor, and also can utilize ANSYS kbench to complete steady-state temperature prediction based on a two-dimensional model of the motor, but the method cannot set a fluid domain, cannot provide a convective heat transfer coefficient and has low accuracy of a simulation result. The implementation approach of the thermal network analysis method is generally to predict the temperature of the motor based on MotorCAD, and can realize the temperature field analysis of the motor in a stable working state. A typical steady state thermal analysis flow for a permanent magnet synchronous machine is shown in fig. 1.
However, the permanent magnet synchronous motor for aviation also has motors such as an engine electric backstepping motor, a starting motor, an EHA actuating motor and the like which work for a short time, even work for a transient state, and for the motors, the previous researches generally believe that the motors do not need to be subjected to temperature field analysis because the motors have short working time and less heat generation; however, as the high power density becomes an important index for measuring the design of the motor, we find that even the motor of the short-time operation system or even the transient operation system generates a large temperature rise in a short time due to the characteristics of the high power density and the high torque density, and therefore, it is necessary to perform temperature field analysis on the motor of the short-time operation system or even the transient operation system.
However, for the motor of the short-time working system, even the transient working system, the condition that the motor is easy to start, brake or overload is analyzed and found, at this time, the copper loss of the stator winding of the motor changes along with the change of the phase current of the stator, the loss of the stator core, the eddy current loss of the permanent magnet, the wind friction loss of the rotor assembly and the friction loss at the bearing change along with the change of the rotating speed of the motor, namely, the loss in the motor changes along with the working time of the motor, and the occupied proportions of different losses are different, the temperature distribution condition of the motor after the transient working system is finished can not be accurately reflected by adopting the method aiming at the motor of the long-time working system, so that a new simulation analysis method is necessary to be provided aiming at the motor of the short-time working system, even the transient working system, and the dynamic parameters of the motor working in a short time can be obtained by means of, and thus a loss versus time curve is obtained. The operating time of the short-time operating system and the transient operating system is generally defined to be within one minute.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a method for predicting the transient temperature of an aviation permanent magnet synchronous motor, which can accurately predict the temperature distribution of the permanent magnet synchronous motor under the condition of an aviation transient working system.
The method includes the steps of designing a two-dimensional electromagnetic field of the motor according to the geometric dimension, material parameters, a working system and load characteristics of the motor, obtaining corresponding electromagnetic parameters, carrying out simulation analysis through a Matlab/Simulink electric drive system, obtaining a three-phase current and motor rotating speed curve of the motor, carrying out transient temperature prediction on the basis of curve fitting, loss calculation through a current source method/voltage source method, three-dimensional model design and finite element model grid division of the motor, cooling and heat dissipation conditions and fluid-solid coupling analysis, and temperature distribution of each part of the motor, obtaining high-precision temperature distribution, and providing help for optimization design of the motor to the maximum extent.
Based on the principle, the technical scheme of the invention is as follows:
the method for predicting the transient temperature of the permanent magnet synchronous motor for aviation is characterized by comprising the following steps: the method comprises the following steps:
step 1: a two-dimensional electromagnetic field model of the permanent magnet synchronous motor is built in electromagnetic simulation software, electromagnetic analysis is carried out by utilizing an external circuit method or a voltage source method, and motor parameters are obtained through calculation; the motor parameters comprise d-axis inductance, q-axis inductance, stator phase resistance, no-load flux linkage, pole pair number, rotational inertia and damping coefficient;
step 2: building a simulation model of the electric drive system, wherein the simulation model comprises a permanent magnet synchronous motor model, a control strategy simulation model, a motor braking module and a load characteristic module; obtaining stator three-phase current waveforms, rotating speed waveforms and output torque waveforms of the permanent magnet synchronous motor through simulation analysis;
and step 3: performing curve fitting on the stator three-phase current waveform and the rotating speed waveform obtained by simulation in the step 2, performing weighted average on fitted curve data according to the step length per second to obtain the amplitude and the rotating speed effective value of the stator phase current in each second of the motor under the whole working system, and obtaining the effective value of the power supply frequency of the motor in each second of the motor under the whole working system according to a formula n of 60f/p, wherein n represents the rotating speed effective value of the motor, f represents the power supply frequency effective value, and p represents the pole pair number of the motor;
and 4, step 4: based on the two-dimensional electromagnetic field model of the permanent magnet synchronous motor established in the step 1, obtaining the stator winding copper loss, the stator core loss and the permanent magnet eddy current loss of the motor in each second in the whole working system by using a current source method according to the amplitude of the stator phase current and the effective value of the power supply frequency of the motor in each second in the whole working system obtained in the step 3;
and 5: establishing a three-dimensional model of the permanent magnet synchronous motor for aviation in three-dimensional modeling software, introducing the three-dimensional model into meshing software, carrying out non-structural meshing on the motor, setting fluid domains inside and outside the motor, and then exporting a motor finite element model with the qualified mesh quality;
step 6: importing the motor finite element model exported in the step 5 into fluid analysis software, and setting a solving type to adopt transient heat; setting a calculation time step length and a total step number of transient thermal analysis; establishing a time-varying function of loss varying with time, endowing the time-varying function and the steady loss to physical structures generating loss in a finite element model of the motor, and endowing the physical structures with actual material properties; the loss changing along with the time is the stator winding copper loss, the stator core loss and the permanent magnet eddy current loss obtained in the step 4; the steady loss comprises wind friction loss of the rotor assembly and mechanical friction loss at a bearing;
and 7: establishing a function of the change of the rotating speed of the motor along with time according to the rotating speed curve data of the motor obtained in the step 3; setting fluid domain boundary conditions of an aviation permanent magnet synchronous motor in a transient working state, setting the rotating speed of the motor by using a time-varying function of the rotating speed of the motor, then performing cyclic iterative computation of load transfer among a fluid domain inside the motor, a fluid domain outside the motor and a solid domain of a structural member of the motor, and when a set convergence condition is met, ending the simulation computation and exporting a simulation result file;
and 8: and (4) carrying out post-processing on the simulation result file to obtain a temperature distribution cloud chart of each part and the whole machine after the transient work of the permanent magnet synchronous motor for aviation is finished and a temperature curve of each part which generates loss in the motor and changes along with time.
Further preferably, the method for predicting the transient temperature of the permanent magnet synchronous motor for aviation is characterized by comprising the following steps: for a surface-mounted permanent magnet synchronous motor, a control strategy simulation model in an electric drive system simulation model adopts a control strategy simulation model combining magnetic field directional control and weak magnetic control; for the built-in permanent magnet synchronous motor, a control strategy simulation model in the electric drive system simulation model adopts a control strategy simulation model combining torque-current ratio maximum control and weak magnetic control.
Advantageous effects
Compared with the prior art, the invention has the beneficial effects that: the invention solves the problem that the working temperature of the permanent magnet synchronous motor for aviation under the transient working condition can not be accurately predicted.
The invention is particularly applied to a permanent magnet synchronous motor for an electromechanical reverse thrust actuation system of an aeroengine of a certain model, and is matched with a motor controller to carry out a temperature test, and the test results are shown in the following table.
TABLE 1 comparison table of actual measurement temperature and simulation calculation temperature of key parts of permanent magnet synchronous motor
| Motor component | Measured maximum temperature (. degree. C.) | Highest temperature of simulation (. degree.C.) | Relative error |
| Casing (CN) | 113.1 | 125.2 | 9.6％ |
| Stator core | 174.0 | 158.9 | 9.56％ |
| Stator winding | 179.8 | 169 | 6.4％ |
| Permanent magnet | 175.4 | 171.6 | 2.2％ |
| Rotor core | 147.5 | 138.9 | 6.2％ |
| Bearing assembly | 84.7 | 85.6 | 1％ |
According to the table 1, the maximum working temperature result measured by a test of key parts of a permanent magnet synchronous motor for an aircraft engine electric reverse thrust actuation system of a certain model and the maximum relative error of the temperature of the key parts of the motor calculated by the transient temperature prediction method provided by the invention are within 10 percent, the feasibility of the transient temperature prediction method of the permanent magnet synchronous motor for the aircraft of the invention is verified, the accuracy of the method can be further improved by optimizing on details, and the accurate simulation of the temperature field under the transient working condition of the permanent magnet synchronous motor for the aircraft is finally realized.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 shows a steady-state thermal analysis process of a permanent magnet synchronous motor;
FIG. 2 is a flow chart;
FIG. 3 Matlab/Simulink System simulation model;
FIG. 4 Motor model in Matlab/Simulink System simulation;
FIG. 5 is a three-phase current waveform during the deployment of the PMSM;
FIG. 6 illustrates a rotational speed waveform during deployment of a PMSM;
FIG. 7 load torque during deployment of the PMSM;
FIG. 8 is a waveform of output torque during deployment of the PMSM;
FIG. 9 is a three-phase current waveform during retraction of a PMSM;
FIG. 10 is a waveform of the rotation speed of the PMSM during the retraction process;
FIG. 11 load torque during retraction of the PMSM;
fig. 12 output torque waveforms during retraction of the permanent magnet synchronous motor;
FIG. 13 is a graph showing the variation of temperature monitoring points of the motor with time step;
fig. 14 is a cloud of temperature distributions of the permanent magnet synchronous motor;
fig. 15 is a sectional view showing a temperature distribution of the permanent magnet synchronous motor.
Detailed Description
The method for predicting the transient working temperature of the permanent magnet synchronous motor for aviation mainly completes the joint simulation of the transient temperature field of the motor based on electromagnetic simulation software, a Matlab/Simulink electric drive system simulation analysis model, ICEM CFD, Fluent and CFD-Post fluid simulation software, and comprises the following specific steps:
step 1: a two-dimensional electromagnetic field model of the permanent magnet synchronous motor is built in electromagnetic simulation software, electromagnetic analysis is carried out by using an external circuit method or a voltage source method, and seven parameters of d-axis inductance, q-axis inductance, stator phase resistance, no-load flux linkage, pole pair number, rotational inertia and damping coefficient of the motor are obtained through calculation.
Step 2: a simulation model of an electric drive system (comprising a permanent magnet synchronous motor and a controller) is built in Matlab/Simulink, and the simulation model comprises a permanent magnet synchronous motor model, a control strategy simulation model, a motor braking module and a load characteristic module. Aiming at a surface-mounted permanent magnet synchronous motor, an electric drive system adopts a control strategy combining magnetic field directional control and weak magnetic control; aiming at the built-in permanent magnet synchronous motor, an electric drive system adopts a control strategy of combining maximum torque-current ratio control and flux weakening control, and combines a braking method of the motor and the actual load characteristic of the motor, a braking module and a load characteristic module of the motor are established in a simulation model of the electric drive system, and then a stator three-phase current waveform, a rotating speed waveform and an output torque waveform of the permanent magnet synchronous motor are obtained through simulation analysis.
And step 3: the method comprises the steps of performing curve fitting on a three-phase current waveform and a rotating speed waveform of a motor obtained by Matlab/Simulink system simulation, performing weighted average on fitted curve data according to step length per second to obtain an amplitude value and a rotating speed effective value of a stator phase current of the motor in each second under the whole work system, and obtaining the effective value of the power supply frequency of the motor in each second under the whole work system based on a relation n of the rotating speed and the frequency of the permanent magnet synchronous motor, wherein n is 60f/p (n represents the rotating speed of the motor, f represents the power supply frequency, and p represents the number of pole pairs of the motor).
And 4, step 4: based on the established two-dimensional electromagnetic field model of the permanent magnet synchronous motor in the electromagnetic simulation software, the stator winding copper loss, the stator core loss and the permanent magnet eddy current loss of the motor in each second in the whole working system are obtained by using a current source method according to the amplitude of the stator phase current and the effective value of the power supply frequency of the motor in each second in the whole working system obtained in the step 3. Although the wind friction loss of the rotor assembly and the mechanical friction loss at the bearing of the motor are related to the rotating speed of the motor, the wind friction loss and the mechanical friction loss are less in the total loss, so the wind friction loss of the rotor assembly and the mechanical loss at the bearing are not considered in the invention temporarily along with the change of the rotating speed of the motor, and the two losses are considered as the steady loss.
And 5: establishing a three-dimensional model of the permanent magnet synchronous motor for aviation in CATIA or UG, guiding a reasonable motor model which accords with fluid dynamics analysis into ICEMCFD, carrying out non-structural meshing on the motor, setting fluid domains inside and outside the motor, checking the mesh quality after finishing the meshing, and guiding out a finite element model of the motor after the mesh quality reaches the standard.
Step 6: and (3) leading the model derived in the step (5) into a Fluent to carry out temperature field analysis of the permanent magnet synchronous motor, firstly adopting transient heat in a solving type, setting a calculating time step and a total step number of the transient heat analysis, establishing a function of loss changing along with time through UDF (user defined function) in the Fluent according to the loss changing along with time obtained in the step (4), endowing the function and the constant loss (wind friction loss of a rotor assembly and mechanical friction loss at a bearing) to a physical structure of the motor generating the loss in a finite element model, and endowing the structure with actual material properties including density, specific heat capacity, heat conductivity and the like of the material.
And 7: and 3, establishing a function of the motor rotating speed changing along with time by using the motor rotating speed obtained in the step 3 through a User Defined Function (UDF) in Fluent, setting a boundary condition of a fluid domain of the permanent magnet synchronous motor for aviation in a transient working state, setting the rotating speed of the motor by using the established function of the motor rotating speed UDF, performing cyclic iterative calculation of load transfer among a fluid domain in the motor, a fluid domain in the external environment of the motor and a solid domain of a motor structural part after the boundary condition is set, and when a set convergence condition is met, finishing the simulation calculation and exporting a simulation result file.
And 8: and (4) importing the result file generated in the step (7) in Post-processing software CFD-Post of Fluent to obtain a temperature distribution cloud chart of each part and the whole machine after the transient work of the permanent magnet synchronous motor for aviation is finished and a temperature curve of each part, which is mainly lost by the motor, changing along with time.
The permanent magnet synchronous motor for the electromechanical reverse thrust device of the aero-engine of a certain model has complex load characteristics, the motor outputs forward torque to push the reverse thrust cover to be close to a set position in the process of unfolding the reverse thrust cover, then a very large braking torque is required to be generated in a very short time to decelerate the reverse thrust cover running at a high speed to zero, and the motor needs to bear rapid change of positive and negative torques in a short time, and belongs to a high-power-density and high-torque-density permanent magnet synchronous motor with transient operation (the total operation time is 11s, wherein the reverse thrust cover needs 5s from a completely folded state to a completely unfolded state, and needs 6s from the completely unfolded state to the completely folded state).
The permanent magnet synchronous motor is high in temperature of the environment, the highest temperature is 70 ℃, good cooling and heat dissipation conditions are not available, the output power is high, the motor is required to be small in size and light in weight, and heat is generated in transient working, the temperature distribution condition of each key part of the motor after the working is finished is calculated by adopting the transient temperature prediction method provided by the invention in the detailed design stage, effective basis is provided for the optimization design of the motor, the iteration times in the research and development process are reduced, and the research and development period is greatly shortened on the premise of ensuring the product quality.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (2)
1. A method for predicting transient temperature of an aviation permanent magnet synchronous motor is characterized by comprising the following steps: the method comprises the following steps:
step 1: a two-dimensional electromagnetic field model of the permanent magnet synchronous motor is built in electromagnetic simulation software, electromagnetic analysis is carried out by utilizing an external circuit method or a voltage source method, and motor parameters are obtained through calculation; the motor parameters comprise d-axis inductance, q-axis inductance, stator phase resistance, no-load flux linkage, pole pair number, rotational inertia and damping coefficient;
step 2: building a simulation model of the electric drive system, wherein the simulation model comprises a permanent magnet synchronous motor model, a control strategy simulation model, a motor braking module and a load characteristic module; obtaining stator three-phase current waveforms, rotating speed waveforms and output torque waveforms of the permanent magnet synchronous motor through simulation analysis;
and step 3: performing curve fitting on the stator three-phase current waveform and the rotating speed waveform obtained by simulation in the step 2, performing weighted average on fitted curve data according to the step length per second to obtain the amplitude and the rotating speed effective value of the stator phase current in each second of the motor under the whole working system, and obtaining the effective value of the power supply frequency of the motor in each second of the motor under the whole working system according to a formula n of 60f/p, wherein n represents the rotating speed effective value of the motor, f represents the power supply frequency effective value, and p represents the pole pair number of the motor;
and 4, step 4: based on the two-dimensional electromagnetic field model of the permanent magnet synchronous motor established in the step 1, obtaining the stator winding copper loss, the stator core loss and the permanent magnet eddy current loss of the motor in each second in the whole working system by using a current source method according to the amplitude of the stator phase current and the effective value of the power supply frequency of the motor in each second in the whole working system obtained in the step 3;
and 5: establishing a three-dimensional model of the permanent magnet synchronous motor for aviation in three-dimensional modeling software, introducing the three-dimensional model into meshing software, carrying out non-structural meshing on the motor, setting fluid domains inside and outside the motor, and then exporting a motor finite element model with the qualified mesh quality;
step 6: importing the motor finite element model exported in the step 5 into fluid analysis software, and setting a solving type to adopt a transient thermal analysis type; setting a calculation time step length and a total step number of transient thermal analysis; establishing a time-varying function of loss varying with time, endowing the time-varying function and the steady loss to physical structures generating loss in a finite element model of the motor, and endowing the physical structures with actual material properties; the loss changing along with the time is the stator winding copper loss, the stator core loss and the permanent magnet eddy current loss obtained in the step 4; the steady loss comprises wind friction loss of the rotor assembly and mechanical friction loss at a bearing;
and 7: establishing a function of the change of the rotating speed of the motor along with time according to the rotating speed curve data of the motor obtained in the step 3; setting fluid domain boundary conditions of an aviation permanent magnet synchronous motor in a transient working state, setting the rotating speed of the motor by using a time-varying function of the rotating speed of the motor, then performing cyclic iterative computation of load transfer among a fluid domain inside the motor, a fluid domain outside the motor and a solid domain of a structural member of the motor, and when a set convergence condition is met, ending the simulation computation and exporting a simulation result file;
and 8: and (4) carrying out post-processing on the simulation result file to obtain a temperature distribution cloud chart of each part and the whole machine after the transient work of the permanent magnet synchronous motor for aviation is finished and a temperature curve of each part which generates loss in the motor and changes along with time.
2. The method for predicting the transient temperature of the permanent magnet synchronous motor for aviation according to claim 1, wherein the method comprises the following steps: for a surface-mounted permanent magnet synchronous motor, a control strategy simulation model in an electric drive system simulation model adopts a control strategy simulation model combining magnetic field directional control and weak magnetic control; for the built-in permanent magnet synchronous motor, a control strategy simulation model in the electric drive system simulation model adopts a control strategy simulation model combining torque-current ratio maximum control and weak magnetic control.
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